Abstract: Disclosed is a space vehicle, such as a satellite, the vehicle including: at least one equipment-carrying module for carrying equipment of the vehicle; at least three posts extending at least partially in the same longitudinal direction and on the periphery of the equipment-carrying module, each post being provided with at least one releasable locking device; and a reinforcing structure which rigidly connects each post transversely to at least two other posts.

Abstract: Disclosed is a space vehicle, such as a satellite, the vehicle including: at least one equipment-carrying module for carrying equipment of the vehicle; at least three posts extending at least partially in the same longitudinal direction and on the periphery of the equipment-carrying module, each post being provided with at least one releasable locking device; and a reinforcing structure which rigidly connects each post transversely to at least two other posts.

Abstract: An antenna reflector for a spacecraft, produced in an elastically deformable way and capable of changing from a folded position to a deployed position at least partly under the action of its own elasticity. The reflector includes at least one fold line, the general direction of which is at least approximately parallel to the axis of the casing and about which said reflector is folded in its folded state.

Abstract: An antenna reflector for a spacecraft includes a radial slot which facilitates stowage of the reflector in the spacecraft. When the reflector is in a folded position, opposing edges of the radial slot overlap in such a way that the reflector assumes an at least approximately conical shape, thereby allowing the reflector to be housed in a casing so as to be oriented vertically in line with the spacecraft.

Abstract: An antenna reflector for a spacecraft is elastically deformable so as to be capable of changing from a folded position, when inside the spacecraft, to a deployed position, outside the spacecraft, at least partly under the action of its own elasticity. The reflector is separated into at least two parts by first opposing slot edges forming a crossing slot, so that in the folded position, the first opposing edges move with respect to each other so as to allow a protruding peripheral part of the reflector to be arranged closer to a longitudinal end of the spacecraft with damaging any portion of the reflector. In one embodiment, the two parts may be further separated by a radial slot which is arranged substantially orthogonal to the crossing slot.